Engineering topics
Publications and source records attributed to Horn, H. J..
The development and characteristics of the Particles and Fields Lunar Subsatellite are discussed. The basic mission is to investigate two problems in space physics: (1) the formation and dynamics of the earth's magnetosphere and (2) the boundary layer of the solar wind as it flows over the lunar surface. Illustrations of the subsatellites and the mission concepts are included.
Developments in the Particles and Fields Lunar Subsatellite Program are reported. The basic purpose of the program is to provide three subsatellites with one for launch with Apollo 15, and one for launch with Apollo 16. At this time all three subsatellites have been completed except for a few minor changes, and the Flight 1 subsatellite has been successfully placed in orbit for the Apollo 15 CSM with all systems performing satisfactorily. The Flight 2 subsatellite is scheduled for launch on March 17, 1972. The Qualification Unit subsatellite has successfully completed its qualification testing.
Iterative guidance mode /IGM/ applied to effective gravity vector prediction, acceleration measurement of noise sensistivity and energy limitations
Cable retrieval and attitude control technique for passive orbiting astronomical observatory tethered to orbiting space station
Iterative guidance mode /IGM/ applied to effective gravity vector prediction, acceleration measurement of noise sensitivity and energy limitations
Optimization of Saturn vehicle, considering interaction of guidance, control and propellant utilization systems
Optimization of Saturn vehicle, considering interaction of guidance, control and propellant utilization systems
Iterative guidance mode to lunar landing
Guidance scheme for vehicle flight from lunar orbit to prescribed point on spherical nonrotating moon
Iterative guidance law for Saturn launch vehicle for lunar landing, examining trajectory optimization
Iterative guidance mode applied to lunar landing for optimization of trajectories for minimum propellant consumption
Optimization of space-vehicle trajectories by use of iterative guidance mode that minimizes midflight recalculation time for new optimum trajectories